Internal Leak Detector Using Temperature and Conductivity Sensors
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Solution Overview
Problem
Current leak detection techniques for rocket engines in space vehicles are limited in effectiveness, particularly in detecting internal leaks and differentiating between actual leakage and false positives, especially in the harsh environment of space where propellants can flash evaporate.
Innovation Solution
A compact leak detector device that combines temperature sensors and electrically conductive wires to detect temperature differences and conductivity changes, allowing for reliable internal leak detection by forming an electric circuit when fluid droplets contact wires, and integrating this device into the rocket engine flow control valve for immediate detection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional leak detection techniques are used for rocket engines, then the detection process is simple, but the detection effectiveness is limited and false positives occur
Solution Approach 1:
The patent combines two different leak detection approaches (temperature-based detection and conductivity-based detection) into a single integrated sensor device. The temperature sensors detect temperature differences caused by propellant leakage, while the conductive wires detect electrical conductivity changes when propellant contacts them. This merging of multiple detection methods within one device improves reliability and reduces false positives without requiring separate detection systems.
Solution Approach 2:
The sensor device performs multiple functions simultaneously: it monitors both temperature differences and electrical conductivity changes to detect leaks. This multi-functional approach allows the single device to provide comprehensive leak detection coverage, improving reliability while avoiding the need for multiple separate devices.
2Reliability
If temperature sensors alone are used for leak detection, then the device structure is simple, but false positive indications of leakage occur
Solution Approach 1:
The device uses temperature sensors to detect temperature differences between the outer surface and inner surface of the housing. When propellant leaks, it causes a temperature drop on the inner surface that is detected by the temperature sensors. This temperature-based feedback mechanism provides continuous monitoring to confirm actual leaks versus false positives.
Solution Approach 2:
The patent merges temperature-based detection with conductivity-based detection in a single device. The conductive wires provide an additional detection mechanism that works alongside the temperature sensors, allowing the system to cross-validate readings and eliminate false positives that would occur with temperature sensors alone.
3Volume of moving object
If a compact sensor device is designed for space applications, then the device size is reduced, but integration into rocket engine components becomes challenging
Solution Approach 1:
The sensor device is designed to be integrated within the flow control valve housing of the rocket engine. The housing of the sensor device serves as part of the valve structure, and the sensor components are nested within the existing valve architecture. This nesting approach minimizes the overall volume required and simplifies integration into the rocket engine system.
Solution Approach 2:
The sensor device housing serves multiple functions: it provides structural support as part of the valve assembly, contains the temperature sensors and conductive wires, and defines the flow passage. This multi-functional design reduces the need for separate components, making the device more compact and easier to integrate into the rocket engine system.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The combined conductivity and temperature measurement approach provides reliable leak detection, avoiding false positives and enabling efficient internal leak detection in space applications, enhancing mission safety and fault detection reliability by promptly identifying leaks before they become catastrophic.
Implementation Method 1
one or more pairs of temperature sensors for detecting a temperature difference between an outside of the housing and the flow passage
Implementation Method 2
an array of electrically conductive wires that extend across the flow passage... detecting a current flowing between one or more of the positive polarity wires and one or more of the negative polarity wires
Implementation Method 3
leakage of liquid that flash evaporates due to exposure to low pressure (e.g., space vacuum)
Data Source
AI summary
This application relates to a leak detector device (100) for detecting an internal leak in a fluid path. The leak detector comprises a housing (110) with a flow passage (120) extending through the housing (110), one or more pairs of temperature sensors (130, 140) for detecting a temperature difference between an outside of the housing (110) and the flow passage (120), one temperature sensor of each pair being arranged towards an outer surface of the housing (110) and the other temperature sensor of the pair being arranged towards an innersurface of the housing (110) that faces the flow passage (120), and an array of electrically conductive wires (150, 160) that extend across the flow passage (120). The array of electrically conductive wires (150, 160) comprises one or more positive polarity wires and one or more negative polarity wires. The application further relates to a corresponding method of leak detection.